CN108502151A - Unit is generated at least two rotor assemblies and the thrust of protective case - Google Patents

Unit is generated at least two rotor assemblies and the thrust of protective case Download PDF

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Publication number
CN108502151A
CN108502151A CN201810150685.6A CN201810150685A CN108502151A CN 108502151 A CN108502151 A CN 108502151A CN 201810150685 A CN201810150685 A CN 201810150685A CN 108502151 A CN108502151 A CN 108502151A
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China
Prior art keywords
rotor
thrust
air duct
protective case
rotor assemblies
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Granted
Application number
CN201810150685.6A
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Chinese (zh)
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CN108502151B (en
Inventor
U·齐塞维特
S·莫斯
M·贝贝塞尔
R·普法勒
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Air Passenger Helicopter Germany Co Ltd
Airbus Helicopters Deutschland GmbH
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Air Passenger Helicopter Germany Co Ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/001—Shrouded propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/26—Ducted or shrouded rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
    • B64C11/48—Units of two or more coaxial propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/70—Constructional aspects of the UAV body
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/13—Propulsion using external fans or propellers
    • B64U50/14—Propulsion using external fans or propellers ducted or shrouded
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D2241/00—NACA type air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/20—Constructional aspects of UAVs for noise reduction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/13—Propulsion using external fans or propellers

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Motor Or Generator Cooling System (AREA)
  • Moulding By Coating Moulds (AREA)
  • Switches With Compound Operations (AREA)
  • Coiling Of Filamentary Materials In General (AREA)
  • Storage Of Web-Like Or Filamentary Materials (AREA)
  • Toys (AREA)
  • Automatic Assembly (AREA)
  • Wind Motors (AREA)

Abstract

Thrust for generating thrust along predetermined direction generates unit (3d), including at least two rotor assemblies (7d, 8d) and accommodate at most one protective case (6d) at least two rotor assemblies (7d, 8d), wherein, protective case (6d) defines cylindrical air duct (20), it is axially defined by air inlet region (20e) and air outlet area (20f) in cylindrical air duct, and wherein, air inlet region (20e) has the geometry to rise and fall in the circumferential direction of cylindrical air duct (20).The thrust generates unit with the improved air dynamic behaviour and performance under side airflow condition.

Description

Unit is generated at least two rotor assemblies and the thrust of protective case
Technical field
The thrust that the present invention relates to a kind of for generating thrust in a predetermined direction generates unit, and thrust generates unit and includes At least two rotor assemblies and protective case.The invention further relates to a kind of multi-rotor aerocraft, band is useful for producing in a predetermined direction At least one thrust of raw thrust generates unit, and it includes at least two rotor assemblies and protective case that thrust, which generates unit,.
Background technology
Such as from 2 551 190 2 551 193 2 551 198 A1, EP 2 234 of A1, EP of A1, EP of document EP 883 A1、WO 2015/028627 A1、US D678 169 S、US 6 568 630 B2、US 8 393 564 B2、US 7 857 253 B2、US 7 946 528 B2、US 8 733 690 B2、US 2007/0034738 A1、US 2013/0118856 Known various conventional more rotors fly in A1, DE 10 2,013 108 207 A1, GB 905 911 and 2,013 06711 U of CN Row device.Also known other multi-rotor aerocrafts from the prior art, such as the CH-47 files heligyro of Boeing, Bell XV-3 tiltrotor aircrafts, Bell XV-22 vert machine and so-called unmanned plane with duct rotor four directions, and particularly Be the such as institute in A1 and 101 451 646 B1 of KR in 2015/0127209 A1, DE 10 2,005 022 706 of document US The so-called quadrotor drone of description.In addition, there is also the research of multi-rotor aerocraft and novels, for example it is sky aviator's skill Sky aviator SF the MK II, Yi Ji of art Co., Ltd (Skyflyer Technology GmbH)《A Fanda (Avatar)》Multiaxis helicopter shown in film.
Each of these conventional multi-rotor aerocrafts generate unit equipped with two or more thrusts, these are pushed away Power generates unit and is arranged for generating the thrust on predetermined direction during the operation of multi-rotor aerocraft.Usually, each It includes one or more rotors or propeller that thrust, which generates unit, and is usually designed for specific state of flight.For example, setting The thrust for counting into properller generates unit and is run under cruising condition optimal, but is designed to the propeller of compound helicopter Thrust generates unit then for hovering or flight forward state optimization, and is embodied as example so-calledEmpennage Thrust generates unit and is specifically designed floating state.
In all these examples, each thrust generates unit and is optimally used for running under the conditions of axial flow, exist At least substantially along rotor axis or the rotation axis of given one or more rotors or propeller orientation and thus be referred to as axis It is run on the airflow direction of airflow direction.However, if each thrust generates unit and runs under side airflow condition, exists Transverse to given one or more rotors or propeller rotation axis orientation and thus be referred to as non axial airflow direction It is run on airflow direction, then the corresponding efficiency of thrust generation unit will be usually substantially reduced.
For example, in the situation for generating the operation of multi-rotor aerocraft of unit with two or more thrusts, such as During the vertical takeoff stage, thrust, which generates unit, to be influenced by axial flow condition.Then, unit production is generated by thrust Raw each thrust vector can be for example by correspondingly rotary thrust generates unit along predetermined direction inclination so that more rotors fly Row device obtains speed and leaves in the floating state of front and be changed into flight forward, wherein thrust generates unit by transverse direction The influence of flow conditions.However, in side airflow condition, in axial flow condition beneficial corresponding duct or protective case by Become unfavorable in the relatively large amount of resistance of generation.In other words, the basis provided in terms of hovering by duct or protective case is excellent Gesture result leads to the disadvantage in flight forward, the disadvantage with the corresponding forward speed of the multi-rotor aerocraft of flight forward increasing Add and increases.
Moreover, it should be noted that under the conditions of axial flow, rotor or propeller with duct, be provided with duct or The rotor or propeller of sheath are compared to isolation equivalent, with similar overall dimensions, i.e. diameter and mean chord or without culvert Road, the rotor or propeller more effectively about 25% to 50% i.e. without duct or protective case.In other words, the presence of duct or protective case increases The given thrust under constant required power has been added to generate unit accordingly generated thrust.Thus, conventional thrust generates unit It is usually provided with and is enclosed in one or more of associated duct or protective case rotor or propeller completely.Classics construction makes The speed caused with corresponding rotor or propeller generates thrust, and duct or protective case is also utilized to generate thrust.
Usually, duct or protective case are limited by fenced annular surface, and fenced annular surface surrounds rotor or propeller Arrangement, so as to improve rotor or the corresponding air dynamic behaviour and performance of propeller.Conventional duct or protective case is usually not It is rotatable, cannot tilt, and height be selected such that given rotor or propeller completely include wherein.
However, must have certain altitude or length with fenced associated rotor or propeller due to duct or protective case and Thus relatively large sized, duct or protective case increase the total weight of corresponding multi-rotor aerocraft due to its size, and due also to Duct or protective case cannot be tilted for adjusting the thrust vector direction on basis and for example during flight forward, i.e. in crossflow Increase resistance in condition.Larger size also results in the larger projection surface that wind and/or fitful wind may be applied to it.This leads Cause the increased overall power requirement of corresponding multi-rotor aerocraft.In addition, if two or more rotors or propeller are for example same Axis one positioning on the other side, then for the given duct or protective case set by these rotors or propeller will need more Big height and can be heavier.In addition, conventional duct or protective case usually active rotation and not must be designed to relative stiffness, This is because usually needing a minimum clearance between rotor or propeller and duct or protective case surface.In addition, respective thrust is produced The conventional duct or protective case of raw unit be unsuitable for the fenced rotor being configured differently or propeller, i.e. with different gradients, The rotor or propeller of position and/or size or diameter.
To sum up, it in the conventional thrust with duct or protective case generates unit, is produced in the operation of axial flow condition The rotor axis for the corresponding rotor or propeller that raw thrust vector generates unit to thrust is aligned and is directed toward running rotor Or the speed field direction that propeller is caused.Rotor or propeller make certain mass-stream accelerate to pass through associated rotor or spiral shell Revolve paddle plane or disk.The caused flow occurred when air passes through rotor or propeller plan or disk accelerate around duct or The corresponding collecting zone of protective case forms negative pressure region, to generate additional thrust.The generation of the additional thrust is by duct or shield Considerable advantage caused by the use of shell, however, its in flight forward, i.e. in side airflow condition due to duct or protective case Generated additional drag and become very unfavorable.Additional drag is directly proportional with corresponding front face area, the front face area By the product limit of the height and width of duct or protective case.Thus, for example, for by being completely embedded into single duct or protective case Two rotors or propeller and the thrust with reversion rotor or propeller construction generates unit, additional drag sets compared to only The thrust generation unit for being equipped with the rotor or propeller that are completely embedded into single duct or protective case is almost double.
5 150 857 A of document US describe a kind of unmanned vehicle (UAV), which, which has, is surrounded by pair Coaxial more blades reversely rotate the annular fuselages of rotors.Annular fuselage defines duct or protective case, and has and be configured to provide The aerofoil profile of high hovering efficiency simultaneously generates the pressure distribution for providing high-lift.Aerofoil profile is symmetrical and is being put down forward suitable for reacting on The unexpected upward pitching moment that the rotation type UAV with duct is undergone in flying.However, the symmetrical duct limited by annular fuselage Or protective case has in flight forward, the disadvantages mentioned above i.e. in side airflow condition.
Invention content
Thus, unit is generated the purpose of the present invention is to provide a kind of new thrust being used in particular for multi-rotor aerocraft, It is with the improved air dynamic behaviour and performance under side airflow condition.
By generating unit solution for generating the thrust of thrust in a predetermined direction, which generates unit and includes the purpose Feature in claim 1.More specifically, generating unit packet for generating the thrust of thrust in a predetermined direction according to the present invention It includes at least two rotor assemblies and accommodates at most one protective case at least two rotor assemblies.Protective case defines cylindrical wind Road, cylindrical air duct are axially defined by air inlet region and air outlet area, wherein air inlet region is in cylinder The geometry of fluctuating is presented in the circumferential direction in air duct.
It should be pointed out that term " protective case " is interpreted as covering term " duct " and " protective case " simultaneously.In other words, in this hair In bright context, term " protective case " interchangeably refers to duct or protective case.
Advantageously, thrust of the invention generates unit and is implemented as the construction of more rotor assemblies with protective case, which causes It is shown under side airflow condition, for example in generating the flight forward of given multi-rotor aerocraft of unit using the thrust of the present invention Write the resistance reduced.The resistance being substantially reduced is not only due to accommodate at most one at least two rotor assemblies in protective case And it is caused that the total height of protective case is significantly reduced, due also to the circumferential direction in the protective case of the present invention, particularly cylindrical air duct On the geometry design of fluctuating of air inlet region itself caused by.
More specifically, the protective case and all associated elements of the present invention it is preferably axially asymmetric, i.e. in the side of protective case It is asymmetric on parallactic angle ψ.In other words, protective case is designed based on the variable factor relative to all associated elements, i.e.,：
Height and azimuth ψ；
Air inlet region radius and azimuth ψ；
Air outlet area radius and azimuth ψ；And/or
The arrangement of additional lifting surfaces and azimuth ψ.
Particularly, the variable height of protective case allows significant advantage, i.e., between vertical takeoff and hovering and flight forward Balance, in vertical takeoff and hovering, with the increase of protective case height, basid efficiency increases, in flight forward, with shield The height of shell reduces, since this reduce the corresponding drag area of protective case, datum drag reduces.
In addition, the weight ratio that the thrust of the present invention generates unit has the list of fenced two rotors or propeller component completely The thrust generation unit of the conventional belt protective case of a protective case is much lower, while flying in axial flow condition, i.e. in corresponding more rotors There is comparable performance in the hovering flight of row device.In fact, it should be pointed out that with completely it is fenced two or more, it is excellent Be selected as reversion rotor or propeller component single protective case conventional belt protective case thrust generate unit with for example with only fenced One in two or more rotors or propeller component and retain other rotors or propeller component and exposed without protective case, i.e. To the protective case of the much shorter of air thrust generate unit, the thrust of all present invention in this way generates the identical thrust pair of unit offer Power characteristic.This is due to the fact that：Above-mentioned additional thrust only by produced by the air inlet region that is limited by protective case, and It is not to be generated by duct or protective case itself.In addition, by least two rotors or propeller component with long protective case and short protective case The corresponding speed field caused to generate the negative pressure domain on air inlet region and is also constructed with long protective case construction and short protective case It is identical.This is similarly applicable for the construction with more rotors or propeller component, and each component is enclosed in minimized height In single associated protective case.
Preferably, the protective case of thrust of the invention generation unit flies in more rotors of the thrust generation unit with the present invention Be used as additional lift equipment in the hovering of row device and flight forward situation, and thus advantageously allow for reducing and be contained in protective case At most one corresponding power consumption at least two rotor assemblies.Further, since protective case increases the effective of rotor assemblies Property, so protective case advantageouslys allow at least reducing at most one basis being contained at least two rotor assemblies therein directly Diameter.In addition, protective case valuably provides effect of screening to be contained at least two rotor assemblies therein at most one, and because And advantageously allow for reducing corresponding rotor noise to the influence on ground.
According to one aspect, thrust of the invention generates unit and can for example be protected by the way that foreign body is arranged by screen encompassing Part, at most one separate foreign body being contained at least two rotor assemblies therein to protection.The foreign body is protected Guard valuably for example prevents personal misuse and accident by preventing the hand of people from being trapped in rotating part, to lead The thrust of the present invention is caused to generate the increased operational safety grade of unit.
Advantageously, at least two rotor groups for limiting different rotor planes are provided by the thrust generation unit for the present invention Part, each rotor assemblies can a positioning rotate on the other side and in a manner of reversely rotating, due to two or more rotors Plane can be bonded to single thrust and generate in unit, so be provided increased safe class and allow to reduce associated The thrust of the overall dimension of multi-rotor aerocraft generates unit, and leads to relatively small aircraft.Preferably, of the invention to push away Power generate at least two rotor assemblies for each defining associated rotor plane or surface of unit coaxially or with point From independent rotor axis and can be angled with respect to each other ground one positioning on the other side.In addition, the thrust production of the present invention Raw unit is suitable for that torque is provided separately since it inverts rotor assemblies, so as to be used to for example have this for yaw manipulation The thrust of invention generates the given multi-rotor aerocraft of unit.
According to preferred embodiment, the axial direction in the cylindrical air duct in height edge in cylindrical air duct is limited at air outlet slit area Between domain and air inlet region, this highly changes in the circumferential direction in cylindrical air duct, wherein the circumferential direction along cylindrical air duct becomes The High definition of the change geometry of the fluctuating of air inlet region.
According to another preferred embodiment, cylindrical air duct is wrapped in the circumferential including leading edge and the rear being diametrically opposed to one another The starboard side shoulder for including port side shoulder and being diametrically opposed to one another, wherein port side shoulder and starboard side shoulder are respectively along cylinder Air duct is arranged circumferentially between leading edge and rear, and wherein, and the height of edge is less than port side shoulder and/or starboard side shoulder Height at portion.
According to another preferred embodiment, the height at rear is less than the height at port side shoulder and/or starboard side shoulder.
According to another preferred embodiment, the height at rear is less than the height of edge.
According to another preferred embodiment, the height at port side shoulder and/or starboard side shoulder is from 0.05*D to 0.5*D Range in select, wherein D defines the diameter in cylindrical air duct.
According to another preferred embodiment, the air inlet region radius of the air inlet region in cylindrical air duct is in cylinder Change in the circumferential direction in air duct, wherein air inlet region radius is in leading edge, rear, port side shoulder and starboard side shoulder At least change between the two.
According to another preferred embodiment, the air outlet area radius of the air outlet area in cylindrical air duct is in cylinder Change in the circumferential direction in air duct, wherein air outlet area radius is in leading edge, rear, port side shoulder and starboard side shoulder At least change between the two.
According to another preferred embodiment, the rear in cylindrical air duct at least opens and is provided with reinforcing element substantially.
According to another preferred embodiment, the rear in cylindrical air duct is equipped with wing flap.
According to another preferred embodiment, the leading edge in cylindrical air duct is provided with additional lifting surfaces.
According to another preferred embodiment, the first rotor assemblies at least two rotor assemblies are arranged in outside cylindrical air duct Portion and adjacent to the air inlet region in cylindrical air duct, wherein protective case accommodates the second rotor at least two rotor assemblies Component.
According to another preferred embodiment, the first rotor assemblies define that the first rotor axis, the second rotor assemblies define Second rotor axis, the first rotor axis and the second rotor axis are coaxially arranged.
According to another preferred embodiment, the first rotor axis and the second rotor axis are to be included between -60 ° to+60 ° Associated oblique angle in range.
The invention further relates to a kind of multi-rotor aerocrafts at least one thrust generation unit including above-mentioned construction such as.
Advantageously, the protective case of thrust of the invention generation unit, which allows to reduce, keeps thrust generation unit of the present invention characteristic The overall dimension of multi-rotor aerocraft of the present invention.In addition, the people for generating unit close to the thrust with protective case are protected against wound Evil can safely and reliably prevent foreign body from generating the damage of unit to running thrust, for example bird collisions or cable are hit, And the overall operation safety of associated multi-rotor aerocraft in midair collision situation can be improved.
In addition, can be by reducing running corresponding blade loading, reduction overall power dissipation, reducing and make an uproar accordingly Sound emission amount and improve the present invention multi-rotor aerocraft hovering and flight forward function and improve corresponding aerodynamics Characteristic, acoustic characteristic and performance.In addition, the corresponding required diameter that thrust generates unit can be reduced.In addition, being changed by protective case itself The promotion of the multi-rotor aerocraft of rare book invention, so as to reduce the overall power needed for the multi-rotor aerocraft of the present invention.
Although it should be pointed out that above with reference to more rotor structures of more rotor assemblies come describe the present invention flight Device, but the aircraft of the present invention by the multiple propeller structure that is similarly effected into multiple propeller components or can be implemented as more Propeller and more rotor structures.More specifically, what rotor typically pivoted completely, and propeller is typically not pivot completely. However, the two can be used in generating thrust and thus for implementing thrust according to the present invention generate unit.As a result, in this description In to any with reference to the reference that can be similarly understood to propeller and propeller arrangement of rotor or rotor structure, to this The multi-rotor aerocraft of invention can similarly be implemented to multiple propeller aircraft and/or multiple propeller and multi-rotor aerocraft.
In other words, the invention mainly relates to a kind of more thrusts to construct, which, which carries, can be selected as individually One positioning on the other side restriction rotor/propeller plan rotor/propeller, for a fenced at most rotor/ The protective case of any rotating part of propeller, at least one motor of each rotor/propeller of driving, wherein each engine It can be isolated, it, should to increase provided safe class, and wherein it is preferred to there are logical connections between battery and motor Logical connection preferably includes Redundancy Design, to increase the safe class in failure situations, and wherein it is preferred to is provided with Battery redundant arrangement with proper security grade in failure situations.
Advantageously, multi-rotor aerocraft of the invention is designed for passenger traffic, and especially suitable for being authorized for It is run in urban area.It is preferably easy to flight, with multiple Redundancy Designs, the safety requirements that meets authorities, save design Cost and only generate lower noise.Preferably, multi-rotor aerocraft of the invention has smaller rotor diameter and light weight Design and fixed incidence angle (angle of incident), although these features of rotor blades cause operation in lower inertia and Nonadjustable torque, but the multi-rotor aerocraft of the present invention is still applied to realize forced landing.
According to one aspect, multi-rotor aerocraft of the invention can hover and include distributed propulsion system.It is also advantageous Ground is designed with spinning ability, this meets the decree about safety failure pattern, such as FAR and EASA detailed rules and regulations other It is required in it is required that, safety failure pattern is up to for entire multi-rotor aerocraft per the pilot time about 1*10-7Locate failure. In aviation field, these safe classes usually ensure grade (DAL) A to D to limit by so-called design.
Preferably, multi-rotor aerocraft of the invention meets authorities and provides to transport the safe class needed for passenger.This is excellent Selection of land is realized by the combination of the following with being associated with：
Each thrust generates at least two individual rotor assemblies of unit；
Redundancy and the battery arrangement of isolation；
The power supply supply of redundancy and harness arrangement；
The physical separation of fundamental power supply management；
Redundancy and the motor of isolation；And
The pitch control and/or RPM of rotor assemblies control.
Description of the drawings
Middle refer to the attached drawing is described below and illustratively summarizes the preferred embodiment of the present invention.In the drawings, identical Or the component and component of phase same-action are indicated by identical reference numeral and thus only description is primary in the following description.
- Fig. 1 shows the stereogram for the multi-rotor aerocraft that unit is generated with multiple exemplary thrusts；
Fig. 2 shows the vertical views of the multi-rotor aerocraft in Fig. 1；
- Fig. 3 show flight forward during Fig. 1 and Fig. 2 in multi-rotor aerocraft side view；
- Fig. 4 shows the front view of the multi-rotor aerocraft in Fig. 3；
- Fig. 5 shows that the thrust of multi-rotor aerocraft with protective case according to the present invention, in Fig. 1 to Fig. 4 generates The stereogram of unit；
- Fig. 6 shows that the thrust in Fig. 5 generates the front view of unit；
- Fig. 7 show the vertical takeoff of the multi-rotor aerocraft in Fig. 1 to Fig. 4 and Fig. 5 during flight forward and Thrust in Fig. 6 generates the partially transparent side view of unit；
- Fig. 8 shows the partially transparent side view of the protective case in Fig. 5 to Fig. 7；
- Fig. 9 shows the stereogram of the protective case in Fig. 8；
- Figure 10 shows the vertical view of the protective case in Fig. 8 and Fig. 9；
- Figure 11 shows the exemplary sectional view of the protective case in Fig. 8 to Figure 10；
- Figure 12 show the vertical takeoff of the multi-rotor aerocraft in Fig. 1 to Fig. 4 and Fig. 5 during flight forward and Thrust in Fig. 6 generates the partially transparent side view of unit；
- Figure 13 shows chart, shows the exemplary controlling party for controlling the multi-rotor aerocraft in Fig. 1 to Fig. 4 Method；
- Figure 14 shows the vertical view of the protective case in Fig. 8 and Figure 10 according to the first variation example；
- Figure 15 show with Fig. 8 to Figure 10 according to the second variation example protective case, Fig. 5 and Fig. 6 thrusts generate unit Partially transparent side view；
Protective case during the vertical takeoff that-Figure 16 shows the multi-rotor aerocraft in Fig. 1 to Fig. 4, in Figure 15 is bowed View；
Figure 17 shows bowing for the protective case during the flight forward of the multi-rotor aerocraft in Fig. 1 to Fig. 4, in Figure 15 View.
Fig. 1 shows the multi-rotor aerocraft 1 with aircraft body 2 according to the present invention.Aircraft body 2 defines Supporting structure, the supporting structure are hereinafter also referred to as the fuselage of multi-rotor aerocraft 1.
Fuselage 2 has the extension on the 1a of longitudinal direction and the extension on transverse direction 1b, and preferably limits internal volume 2a, content Product 2a is at least suitable for passenger traffic so that multi-rotor aerocraft 1 is suitable for passenger traffic as a whole.Internal volume 2a is preferably also Suitable for receiving operation electrical equipment, for example it is that multi-rotor aerocraft 1 runs required energy storage system.
It is electrically set suitable for passenger traffic and receiving operation it should be pointed out that those skilled in the art can be easily obtained The representative configuration of standby internal volume 2a, and this is generally considered as meeting to need about the applicable decree of passenger traffic and certification It wants.Thus, since these constructions of internal volume 2a are not the parts of the present invention, so for simplicity to it without retouching It states.
According to one aspect, multi-rotor aerocraft 1 includes that multiple thrusts generate unit 3.Preferably, multiple thrusts generate unit 3 include at least two and preferably four thrusts generate unit 3a, 3b, 3d, 3d.Thrust generates unit 3a, 3b, 3c, 3d by reality It is applied to and generates thrust (9 in Fig. 3) in operation so that multi-rotor aerocraft 1 can hover in air and with any Direction is flown forward or backward.
Preferably, thrust generates and is connected to fuselage 2 in unit 3a, 3b, 3c, 3d structure.For example, this passes through multiple structure branch Bearing member 4 is realized.More specifically, thrust generates unit 3a is preferably connected to fuselage 2, via structure via structural support member 4a Supporting member 4b is connected to thrust and generates unit 3b, is connected to thrust generation unit 3c via structural support member 4c and via structure Supporting member 4d is connected to thrust and generates unit 3d, wherein structural support member 4a, 4b, 4c, 4d limit multiple structural support members 4.
Preferably, it includes relevant protective case that at least one thrust, which generates unit 3a, 3b, 3c, 3d, to improve the air of lower section Dynamic performance simultaneously increases safety in operation.For example, multiple protective case units 6 be shown with four separation protective case 6a, 6b, 6c、6d.Schematically, protective case 6a is associated with thrust generation unit 3a, and protective case 6b is associated with thrust generation unit 3b, protective case 6c is associated with thrust generation unit 3c, and protective case 6d is associated with thrust generation unit 3d.
Protective case 6a, 6b, 6c, 6d can be made of simple sheet metal.However, according to one aspect, protective case 6a, 6b, 6c, 6d With complicated geometry, such as below with reference to geometry described in Fig. 5.
In addition, protective case 6a, 6b, 6c, 6d can be connected to fuselage 2 together with structural support member 4a, 4b, 4c, 4d, to reinforce Thrust generates the connection between unit 3a, 3b, 3c, 3d and fuselage 2.Instead, it is possible to which only protective case 6a, 6b, 6c, 6d is connected to machine Body 2.
According to one aspect, at least one and preferably each thrust generates unit 3a, 3b, 3c, 3d and is equipped at least two Rotor assemblies.For example, thrust generates unit 3a equipments there are two rotor assemblies 7a, 8a, thrust generates there are two unit 3b equipments Rotor assemblies 7b, 8b, thrust generate unit 3c equipments there are two rotor assemblies 7c, 8c, and thrust generates there are two unit 3d equipments Rotor assemblies 7d, 8d.Rotor assemblies 7a, 7b, 7c, 7d schematically define multiple upper rotor assemblies 7, rotor assemblies 8a, 8b, 8c, 8d schematically define multiple lower rotor assemblies 8.
Multiple upper rotor assemblies 7 and lower rotor assemblies 8 are preferably connected to multiple structures by multiple gear-box radome fairings 5 Supporting member 4.Schematically, upper rotor assemblies 7a and lower rotor assemblies 8a are connected to structural support member by gear-box radome fairing 5a 4a, upper rotor assemblies 7b and lower rotor assemblies 8b are connected to structural support member 4b, upper rotor assemblies by gear-box radome fairing 5b 7c and lower rotor assemblies 8c is connected to structural support member 4c, upper rotor assemblies 7d and lower rotor assemblies by gear-box radome fairing 5c 8d is connected to structural support member 4d by gear-box radome fairing 5d.
Preferably, each of upper rotor assemblies 7a, 7b, 7c, 7d define associated upper rotor plane (in Fig. 7 21), each of lower rotor assemblies 8a, 8b, 8c, 8d define associated lower rotor plane (22 in Fig. 7).Preferably, Upper rotor assemblies 7a, 7b, 7c, 7d and lower rotor assemblies 8a, 8b, 8c, 8d are defined and are respectively received in protective case 6a, 6b, 6c, 6d Pairs of rotor assemblies 7a, 8a up and down；7b、8b；7c、8c；7d, 8d so that associated upper rotor plane and lower rotor are flat Face (21,22 in Fig. 6) is located inside protective case 6a, 6b, 6c, 6d of multi-rotor aerocraft 1.
According to one aspect, multi-rotor aerocraft 1 includes aircraft operation structure and redundant safety framework.Aircraft operation knot Structure is preferably adapted to operation of the multi-rotor aerocraft 1 in failure-free operation pattern, and redundant safety framework is preferably at least suitable for Operation of the multi-rotor aerocraft 1 in the failure situations of aircraft operation structure.Particularly, redundant safety framework is arranged to preferably Ground meets the applicable decree and certification needs about passenger traffic.
Preferably, aircraft operation structure includes upper rotor assemblies 7a, 7b, 7c, 7d and lower rotor assemblies 8a, 8b, 8c, 8d At least first part, redundant safety framework includes upper rotor assemblies 7a, 7b, 7c, 7d and lower rotor assemblies 8a, 8b, 8c, 8d At least second part.Preferably, each thrust generate the 7a, 8a of rotor assemblies up and down of unit 3a, 3b, 3c, 3d, 7b, 8b, 7c, First in 8c, 7d, 8d is associated with aircraft operation structure, and second associated with redundant safety framework.On for example, Rotor assemblies 7a, 7b, 7c, 7d are associated with aircraft operation structure, lower rotor assemblies 8a, 8b, 8c, 8d and redundant safety framework It is associated.Thus, at least in the situation of upper rotor assemblies 7a, 7b, 7c, 7d failure, lower rotor assemblies 8a, 8b, 8c, 8d operation Multi-rotor aerocraft 1, to avoid for example its fall.
However, it is noted that upper rotor assemblies 7a, 7b, 7c, 7d be associated with aircraft operation structure and lower rotor group Part 8a, 8b, 8c, 8d above-mentioned construction associated with redundant safety framework only as example come describe rather than by the present invention limit It is formed on this.Alternatively, the similar interrelational form that may have and imagine replacement.For example, rotor assemblies 7a, 7c, 8b, 8d can be with flights Device, which operates structure, to be associated, and rotor assemblies 8a, 8c, 7b, 7d are associated with redundant safety framework.For example, all upper rotor groups Part 7a, 7b, 7c, 7d and lower rotor assemblies 8a, 8b, 8c, 8d can be related to aircraft operation structure and/or redundant safety framework etc. Connection.Those skilled in the art can be easily obtained the interrelational form of replacement as a result, these can similarly be expected and be considered as The part of the present invention.
Fig. 2 shows more rotor flyings in the Fig. 1 for generating unit 3a, 3b, 3c, 3d with the thrust for being connected to fuselage 2 Device 1.Thrust generates unit 3a, 3b, 3c, 3d and respectively includes rotor assemblies 7a, 8a up and down；7b、8b；7c、8c；7d, 8d, they are excellent Selection of land is along rotor axis (12 in Fig. 3 and Fig. 4) side-by-side configuration arrangement to coincide.Preferably, upper rotor assemblies 7a, 7b, 7c, 7d It is arranged in above lower rotor assemblies 8a, 8b, 8c, 8d so that upper and lower rotor assemblies 7a, 8a；7b、8b；7c、8c；7d, 8d are stacked, I.e. on the other side along arrangement of the rotor axis (12 in Fig. 3 and Fig. 4) to coincide.It is replaced however, can also similarly imagine The construction in generation, such as axial displacement rotor axis.
As can be from further being seen in Fig. 2, thrust generates unit 3a, 3b, 3c, 3d all illustratively relative to fuselage 2 lateral arrangements, i.e., along its longitudinal direction, 1a looks and is arranged in the left or right side of fuselage 2.Schematically, as shown in Figure 2, left side is right The upside of fuselage 2 should be corresponded in the downside of fuselage 2, right side.In addition, fuselage 2 is illustratively implemented to make lateral arrangement It is at least rough trapezoidal that thrust generates unit 3a, 3b, 3c, 3d restriction.
However, it is noted that the exemplary arrangement only describes as example rather than limits the invention to this. Alternatively, other arrangements are also possible that and it can also be envisaged that similar to similar arrangements.For example, thrust generate unit 3a, 3b, 3c, Two in 3d can be arranged at the front waist section and rear section of fuselage 2, etc..
Fig. 3 shows the multi-rotor aerocraft 1 in Fig. 1 and Fig. 2 in exemplary failure-free operation pattern.Show at this In example property failure-free operation pattern, multiple thrusts generate unit 3 and are generated by multiple upper rotor assemblies 7 and/or lower rotor assemblies 8 The air-flow of airflow direction 9 is generated along thrust, multiple upper rotor assemblies 7 and/or lower rotor assemblies 8 are suitable for making multi-rotor aerocraft 1 takes off from ground 10.
Each of multiple upper rotor assemblies 7 define the first rotor axis, each restriction in multiple lower rotor assemblies 8 The second rotor axis.Preferably, the first rotor axis and the second rotor axis are respectively coinciding, i.e. coaxially arranged, are made It obtains multiple upper rotor assemblies 7 and lower rotor assemblies 8 defines multiple coaxially arranged rotor axis 12.Schematically, upper rotor Component 7c and lower rotor assemblies 8c defines that being collectively referred to as the first of rotor axis 12c coincides the rotor shaft to coincide with second Line, upper rotor assemblies 7d and lower rotor assemblies 8d, which are defined, to be collectively referred to as the first of rotor axis 12d and coincides to coincide with second Rotor axis.
However, can also similarly imagine other constructions.For example, each rotor axis can be parallel to arrangement, etc. each other.
Preferably, multiple thrusts generate units 3 with multiple vertical inclination angles 11 multi-rotor aerocraft 1 longitudinal 1a updips Tiltedly, to reduce the overall inclination on longitudinal 1a of multi-rotor aerocraft 1 during flight forward, and increase more rotors and fly The navigability of row device 1.Multiple vertical inclination angles 11 be schematically limited at the vertical reference line 10a of multi-rotor aerocraft 1 with Between multiple coaxially arranged rotor axis 12.Preferably, the possibility of the multiple vertical inclination angles 11 and quantity realized depends on Set thrust generates the basic quantity of unit.
More specifically, according to one aspect, multiple thrusts are generated at least one of unit 3 and are being revolved with first longitudinal direction inclination angle more Tilted on longitudinal 1a of rotor aircraft 1, first longitudinal direction inclination angle be limited to the vertical reference line 10a of multi-rotor aerocraft 1 with it is multiple Thrust generates the rotor shaft that at least one thrust in unit 3 generates the first rotor axis to coincide of unit and second coincides Between line.First longitudinal direction inclination angle is preferably incorporated in the range between -45 ° to+80 °, and preferably equivalent to 7 °.
Schematically, multiple thrusts are generated the thrust generation unit 3c in unit 3 and are tilted with first longitudinal direction inclination angle 11a, the One vertical inclination angle 11a is limited between vertical reference line 10a and rotor axis 12c, wherein first longitudinal direction inclination angle 11a is preferably It is included in the range between -45 ° to+80 °, and preferably equivalent to 7 °.However, it is noted that multiple in Fig. 1 and Fig. 2 Thrust generates the thrust in unit 3 and generates unit 3a preferably also with first longitudinal direction inclination angle 11a inclinations.
According to one aspect, multiple thrusts generate at least one of unit 3 with second longitudinal direction inclination angle in multi-rotor aerocraft 1 Longitudinal 1a on tilt, second longitudinal direction inclination angle be limited to vertical reference line 10a and multiple thrusts generate in unit 3 this at least one Between the rotor axis that a thrust generates the first rotor axis to coincide of unit and second coincides.Second longitudinal direction inclination angle is preferably It is also included in the range between -45 ° to+80 °, and preferably equivalent to 7 °.
Schematically, multiple thrusts are generated the thrust generation unit 3d in unit 3 and are tilted with second longitudinal direction inclination angle 11b, the Two vertical inclination angle 11b are limited between vertical reference line 10a and rotor axis 12d, wherein second longitudinal direction inclination angle 11b is preferably It is included in the range between -45 ° to+80 °, and preferably equivalent to 7 °.However, it is noted that multiple in Fig. 1 and Fig. 2 Thrust generates the thrust in unit 3 and generates unit 3b preferably also with second longitudinal direction inclination angle 11b inclinations.
Fig. 4 shows the multi-rotor aerocraft 1 with fuselage 2 in Fig. 3, and schematically, 2 width of fuselage is 2b.Fuselage 2 Width 2b be defined as being orthogonal to the corresponding outermost left-hand face of the fuselage 2 that longitudinal 1a of multi-rotor aerocraft 1 is measured with most Maximum distance between external right side surface.
Multi-rotor aerocraft 1 is illustratively shown as source in failure-free operation pattern again, wherein multiple thrusts generate Unit 3 generates the air-flow that airflow direction 9 is generated along thrust by multiple upper rotor assemblies 7 and lower rotor assemblies 8.Such as above with reference to Described in Fig. 3, upper rotor assemblies 7c and lower rotor assemblies 8c define rotor axis 12c, upper rotor assemblies 7d and lower rotor Component 8d defines rotor axis 12d.
In addition, upper rotor assemblies 7a and lower rotor assemblies 8a are illustratively defined and are collectively referred to as rotor axis 12a's The first rotor axis to coincide and the second rotor axis for coinciding, upper rotor assemblies 7b and lower rotor assemblies 8b define common Referred to as the first of rotor axis 12b the rotor axis to coincide and the second rotor axis for coinciding.It is to be pointed out that rotor axis 12a, 12b, 12c, 12d are preferably implemented as reducing overall complexity, system weight and the dimensioning of multi-rotor aerocraft 1 It is very little.
Preferably, multiple thrusts generate units 3 with multiple cross dips 13 multi-rotor aerocraft 1 lateral 1b updips Tiltedly, to provide the fitful wind sensibility of reduction and increase the navigability of multi-rotor aerocraft 1.Multiple cross dips 13 are schematic Ground is limited between the vertical reference line 10a of multi-rotor aerocraft 1 and multiple coaxially arranged rotor axis 12.Preferably, The possibility of multiple cross dips 13 and the quantity realized depend on the basic quantity of set thrust generation unit.
More specifically, according to one aspect, multiple thrusts are generated at least one of unit 3 and are being revolved with the first cross dip more Tilted on the lateral 1b of rotor aircraft 1, the first cross dip be limited to the vertical reference line 10a of multi-rotor aerocraft 1 with it is multiple Thrust generates the rotor shaft that at least one thrust in unit 3 generates the first rotor axis to coincide of unit and second coincides Between line.First cross dip is preferably incorporated in the range between -45 ° to+80 °, and preferably equivalent to 5 °.
Schematically, multiple thrusts are generated the thrust generation unit 3a in unit 3 and are tilted with the first cross dip 13a, the One cross dip 13a is limited between vertical reference line 10a and rotor axis 12a, wherein the first cross dip 13a is preferably It is included in the range between -45 ° to+80 °, and preferably equivalent to 5 °.However, it is noted that multiple in Fig. 1 and Fig. 2 Thrust generates the thrust in unit 3 and generates unit 3c preferably also with the first cross dip 13a inclinations.
According to one aspect, multiple thrusts generate at least one of unit 3 with the second cross dip in multi-rotor aerocraft 1 Lateral 1b on tilt, the second cross dip be limited to the vertical reference line 10a of multi-rotor aerocraft 1 generated with multiple thrusts it is single Between the rotor axis that at least one thrust in member 3 generates the first rotor axis to coincide of unit and second coincides.The Two cross dips are preferably incorporated in the range between -45 ° to+80 °, and preferably equivalent to 5 °.
Schematically, multiple thrusts are generated the thrust generation unit 3b in unit 3 and are tilted with the second cross dip 13b, the Two cross dip 13b are limited between vertical reference line 10a and rotor axis 12b, wherein the second cross dip 13b is preferably It is included in the range between -45 ° to+80 °, and preferably equivalent to 5 °.However, it is noted that multiple in Fig. 1 and Fig. 2 Thrust generates the thrust in unit 3 and generates unit 3d preferably also with the second cross dip 13b inclinations.
Fig. 5 shows that the thrust in aforementioned figures generates unit 3d, thrust generate unit 3d with rotor assemblies 7d thereon, Its lower rotor assemblies 8d, its gear-box radome fairing 5d and its protective case 6d, for further showing its representative configuration.However, answering , it is noted that the thrust in aforementioned figures, which generates unit 3a, 3b, 3c, preferably includes similar construction, for simplicity, push away Power generates representatives of the unit 3d only as all thrusts generation unit 3a, 3b, 3c, 3d and is described.
Preferably, protective case 6d is configured with supporting structure 16, and supporting structure 16 can be by simply suppressing the metal sheet system of bending At.Supporting structure 16 is preferably provided with internal volume, which can be used, for example, as the multi-rotor aerocraft 1 in aforementioned figures The storage volumes of battery system.Schematically, protective case 6d and the more specifically receiving of a supporting structure 16 at most lower rotor group Part for example descends rotor assemblies 8d.Schematically, lower rotor assemblies 8d include at least two, such as three rotor blade 19a, 19b, 19c, for generating thrust in operation.Similarly, upper rotor assemblies 7d preferably also include at least two, such as three Rotor blade 18a, 18b, 18c, for generating thrust in operation.
Further, it is preferable to be arranged at least one first engine 14a for driving rotor blade 18a, 18b in operation, 18c, i.e. upper rotor assemblies 7d, and be arranged at least one second engine 14b for driving rotor blade 19a in operation, 19b, 19c, rotor assemblies 8d is descended.At least one first engine 14a is preferably grasped with the aircraft described above with reference to Fig. 1 It is associated to make structure, at least one first engine 14b is preferably related to the redundant safety framework described above with reference to Fig. 1 Connection.Schematically, at least one first engine 14a and the second engine 14b are arranged in inside gear-box radome fairing 5d, and because And it is surrounded by gear-box radome fairing 5d.
It should be pointed out that optionally, one or more gear-boxes can be introduced at least one first engine 14a and second Engine 14b and rotor blade 18a, 18b, 18c or 19a, between 19b, 19c.By optionally introducing one or more gears The operational efficiency of case, at least one first engine 14a and the second engine 14b may increase since its rotating speed increases.
It should be noted also that at least one first engine 14a and the second engine 14b may be by can be in operation Any suitable engine for generating torque realizes, all turbines in this way of engine, diesel oil (Diesel) engine, etc. appearances cycle (Otto) motor, motor etc., and engine can be connected to rotor blade 18a, 18b, 18c or 19a, 19b, 19c, for transporting These rotor blades 18a, 18b, 18c or 19a, 19b, 19c, i.e. upper rotor assemblies 7d or lower rotor assemblies 8d are rotated in row.So And since these engines are well known and simultaneously non-present invention a part to those skilled in the art, for succinct For the sake of, these engines are not more fully described.
Preferably, upper rotor assemblies 7d is suitable for surrounding the first rotor axis 12e 15a rotations along the first direction of rotation in operation Turn.Similarly, lower rotor assemblies 8d is suitable for rotating along the second direction of rotation 15b around rotor axis 12d in operation, rotor shaft Line 12d schematically defines the second rotor axis.Schematically, the first direction of rotation 15a and the second direction of rotation 16b are preferred Ground is opposite each other.
According to one aspect, the first rotor axis 12e and the second rotor axis 12d can be with associated inclination angle 21a, 22a phases Corresponding fore-and-aft tilt for protective case 6d, this is longitudinal schematically corresponding to the second rotor axis 12d.Associated inclination angle 21a, 22a is preferably incorporated in the range between -60 ° to+60 °.More specifically, associated inclination angle 21a be preferably incorporated in- In range between 10 ° to+45 °, associated inclination angle 22a is preferably incorporated in the range between -5 ° to+5 °.Schematically Ground, the first rotor axis 12e and thus upper rotor assemblies 7d with e.g., about 30 ° of associated inclination angle 21a relative to second Rotor axis 12d and thus descend rotor assemblies 8d tilt.
It at least goes up rotor assemblies 7d and more particularly its rotor blade 18a, 18b, 18c may be provided with optional pitch Variable quantity 17.Similarly, lower rotor assemblies 8d, i.e. its rotor blade 19a, 19b, 19c may also set up this optional pitch Variable quantity.In this case, can in operation by pitch variation, by RPM (rotating speed) change or by pitch variation and RPM variations are combined to realize that the thrust to generated in Fig. 3 and Fig. 4 generates the control of the air-flow of airflow direction 9.
On the contrary, if upper rotor assemblies 7d and lower rotor assemblies 8d are not provided with this optional pitch variation, for example, such as Fruit rotor blade 18a, 18b, 18c or 19a, 19b, 19c are implemented as fixedpiston blade, then cannot execute and change by pitch The air-flow of the thrust generation airflow direction 9 to produced in Fig. 3 and Fig. 4 controls in operation.In this case, only RPM variations can be used to control the pushing away in Fig. 3 and Fig. 4 caused by upper rotor assemblies 7d and lower rotor assemblies 8d in operation Power generates the air-flow of airflow direction 9.
Preferably, each upper rotor assemblies 7d and lower rotor assemblies 8d has individual size, and the machine in a diameter of Fig. 4 0.05 to 6 times of body width 2b, infra for the diameter is denoted as W for the sake of simple.In other words, upper rotor assemblies 7d is under Diameter in each of rotor assemblies 8d is preferably in the range of 0.05*W to 6*W, and preferably equivalent to 1.5*W.
According to one aspect, protective case 6d defines cylindrical air duct 20, cylindrical air duct 20 by supporting structure 16 schematically It is radially defined.It is preferably axially defined by air inlet region 20e and air outlet area 20f in cylindrical air duct 20.In circle The outside of the cylindricality air duct 20 and air inlet region 20e for preferably lying adjacent to cylindrical air duct 20 is preferably arranged with the first rotor Component 7d.
It should be pointed out that air duct 20 is only designated as " cylinder " air duct as example, rather than correspondingly limit this Invention.In other words, although " cylinder " shape in " air duct " means from air inlet region 20e to air outlet area 20f Equal radii along entire air duct 20, but can similarly imagine the construction of replacement.For example, air duct 20 can be in frustum form, Make its radius bigger, etc. than in air inlet region 20e in air outlet area 20f.It is accordingly to be appreciated that table " cylindrical air duct " is stated also to be intended to cover this alternative constructions in air duct 20.
Preferably the geometry to rise and fall is presented along the circumferential of cylindrical air duct 20 in air inlet region 20e.More specifically, The geometry of the fluctuating means, when moving upwards in the week in cylindrical air duct 20, to execute when along air inlet region 20e Volt acts or wave-like motion.
Schematically, protective case 6d, i.e. cylindrical air duct 20 have leading edge 20a and rear 20b.For the sake of clear, answer , it is noted that leading edge 20a is the flight forward of protective case 6d, the i.e. multi-rotor aerocraft in Fig. 1 to Fig. 4 in cylindrical air duct 20 Period is arranged in the edge in upstream position relative to rear 20b.In addition, protective case 6d, i.e. cylinder air duct 20 preferably have Port side shoulder 20c at air inlet region 20e and starboard side shoulder 20d.
More specifically, in protective case 6d, i.e. in the circumferential direction in cylindrical air duct 20, leading edge 20a is diametrically opposite with rear 20b, And port side shoulder 20c is diametrically opposite with starboard side shoulder 20d.In addition, port side shoulder 20c and starboard side shoulder 20d are each Comfortable protective case 6d, i.e. cylinder air duct 20 are upwardly arranged between leading edge 20a and rear 20b in week.
Fig. 6 shows that the thrust in Fig. 5 generates unit 3d, the fluctuating for further showing air inlet region 20e Geometry, thrust generate unit 3d with rotor assemblies 7d thereon, its lower rotor assemblies 8d and its restriction cylinder air duct 20 Protective case 6d, cylindrical air duct 20 is preferably axially defined by air inlet region 20e and air outlet area 20f.Fig. 6 is also Show that rotor assemblies 7d is tilted relative to lower rotor assemblies 8d with associated inclination angle 21a.
Fig. 7 shows that the thrust with upper rotor assemblies 7d and lower rotor assemblies 8d in Fig. 5 and Fig. 6 generates unit 3d's Schematic diagram, upper rotor assemblies 7d and lower rotor assemblies 8d are around its respective rotor axis 12e, 12d rotation.Preferably, upper rotation Wing component 7d and lower rotor assemblies 8d limit the rotor plane 21,22 of separation, to reach required safe class and satisfactory Flight mechanical performance.Schematically, rotor plane 21,22 1 is arranged on the other side.Preferably, rotor plane 21, Preset distance between 22 is included in 0.01*DR to the range between 2*DR, and preferably equivalent to 0.17*D, wherein DR is limited The diameter of the second rotor assemblies 8d is determined.
As described above, protective case 6d defines cylindrical air duct 20, cylindrical air duct 20 is by air inlet region 20e and air Exit region 20f is axially defined.Lower rotor assemblies 8d is arranged in inside protective case 6d, and upper rotor assemblies 7d is arranged in outside protective case 6d Portion i.e. outside cylindrical air duct 20, and preferably lies adjacent to air inlet region 20e.
In the operation that thrust generates unit 3d, air inlet region 20e preferably act as air collector, and thus It is hereinafter also referred to as clarity " collector 20e ".Air outlet area 20f may but not necessarily be carried out and make With for diffuser, and thus hereinafter it is also referred to as clarity " diffuser 20f ".
The part (A) of Fig. 7 shows the multi-rotor aerocraft 1 in Fig. 1 to Fig. 4 under the conditions of axial flow, i.e. vertical Thrust generates the exemplary operation of unit 3d during taking off and hovering.However, with Fig. 5 and Fig. 6 on the contrary, rotor axis 12e, 12d Illustratively it is arranged coaxially to each other.
Schematically, under the conditions of axial flow, axial flow 23a enters via collector 20e in cylindrical air duct 20, It is accelerated by upper rotor assemblies 7d and lower rotor assemblies 8d and leaves cylindrical air duct 20 via diffuser 20f.It should be noted that It is, since air-flow 23a is disposed at least substantially parallel to coaxially arranged rotor axis 12e, 12d orientation, so air-flow 23a is referred to as " axial direction " air-flow.
Axial flow 23a itself generates thrust and is generated by acting on protective case 6d, i.e. cylinder air duct 20 in turn Additional thrust.This will lead to the gross thrust shown in thrust vector 23, to allow the multi-rotor aerocraft in Fig. 1 to Fig. 41 It rises (taking off).It should be pointed out that under same thrust grade, the first engine 14a of at least one of Fig. 5 and Fig. 6 and the Corresponding power amount in engine with two 14b drivings needed for rotor assemblies 7d and lower rotor assemblies 8d will be substantially less than driving and not protect The upper rotor assemblies 7d and the power needed for lower rotor assemblies 8d for covering 6d.
The part (B) of Fig. 7 shows the multi-rotor aerocraft 1 in Fig. 1 to Fig. 4 under side airflow condition, i.e. forward During flight thrust generates the exemplary operation of unit 3d.Schematically, rotor axis 12e, 12d still according to part (A) each other It is coaxially arranged, but crossflow 23b enters in cylindrical air duct 20 via collector 20e, by upper rotor assemblies 7d now It is accelerated with lower rotor assemblies 8d and leaves cylindrical air duct 20 via diffuser 20f.It should be pointed out that extremely due to air-flow 23a It is few substantially to be oriented transverse to the direction of coaxially arranged rotor axis 12e, 12d, so air-flow 23a is referred to as " transverse direction " gas Stream.
In order to allow thrust with good grounds part (B) generate the multi-rotor aerocraft 1 in Fig. 1 to Fig. 2 of unit 3d to Preceding flight, it is preferable that the crossflow 23b in cylindrical air duct 20 is controlled using RPM variable quantities.More specifically, it is preferable to ground, Upper rotor assemblies 7d is rotated than lower rotor assemblies 8d around rotor axis 12d around the 12e rotations of rotor axis, rotary speed It is high.Thus, still the basic orientation of the gross thrust shown in thrust vector 23 shown in part (A) will be redirected to part (C) shown in, to allow the flight forward of the multi-rotor aerocraft 1 in Fig. 1 to Fig. 4.
The part (C) of Fig. 7 shows the multi-rotor aerocraft 1 of Fig. 1 to Fig. 4 according to the present invention in side airflow condition Under, i.e. thrust generates the another exemplary operation of unit 3d during flight forward, wherein according to the crossflow of part (B) 23b via collector 20e enter cylindrical air duct 20, it is accelerated by upper rotor assemblies 7d and lower rotor assemblies 8d and via Diffuser 20f leaves cylindrical air duct 20.However, with part (B) on the contrary, above with reference to described in Fig. 5 and Fig. 6, rotor shaft Line 12e is existing to be tilted with inclination angle 21a.Thus, thrust vector 23 is redirected as illustrated, to allow Fig. 1 extremely The improved flight forward condition of multi-rotor aerocraft 1 in Fig. 4.
Fig. 8 shows that the thrust with protective case 6d in Fig. 5 and Fig. 6 generates another schematic diagram of unit 3d, protective case 6d limits Fixed cylinder air duct 20, cylindrical air duct 20 is preferably axially defined by collector 20e and diffuser 20f and includes leading edge 20a, rear 20b, port side shoulder 20c and starboard side shoulder 20d.However, for clarity, rotor assemblies 7d is omitted With the diagram of lower rotor assemblies 8d.
According to one aspect, cylindrical air duct 20 has the axial direction along cylindrical air duct 20, is limited to diffuser 20f and collects Height between device 20e, this is highly along the circumferential direction variation in cylindrical air duct 20.This highly becomes in the circumferential direction in cylindrical air duct 20 Change, and thus define as described above with reference to Figure 5 collector 20e fluctuating geometry.
More specifically, the height 24a at leading edge 20a is preferably less than port side shoulder 20c and/or starboard side shoulder 20d The height 24c at place.In addition, the height 24b at rear 20b is preferably less than port side shoulder 20c and/or starboard side shoulder 20d The height 24c at place.In addition, the height 24b at rear 20b is preferably less than the height 24a at leading edge 20a.According to one aspect, left Height 24c at topside shoulder 20c and/or starboard side shoulder 20d is selected in the range from 0.05*D to 0.5*D, wherein D It defines the diameter in cylindrical air duct 20, be preferably interior diameter (20g in Figure 10).
According to one aspect, circumferential variation of the radius of the collector 20e in cylindrical air duct 20 along cylindrical air duct 20.Change speech It, collector 20e is preferably not provided with flat top edge, i.e. it is away from the edge that diffuser 20f is directed toward, but carries blunt circle Top edge.Preferably, the radius for being hereinafter also referred to as the collector 20e of " collector radius " for clarity exists At least changing between the two in leading edge 20a, rear 20b, port side shoulder 20c and starboard side shoulder 20d.
Preferably, the collector radius 25a at leading edge 20a is selected in the range from 0.01*D to 0.25*D, rear 20b The collector radius 25b at place is selected in the range from 0 to 0.25*D, at port side shoulder 20c and/or starboard side shoulder 20d Collector radius 25c selected in the range from 0.01*D to 0.25*D.As described above, D defines cylindrical air duct 20 Diameter, preferably interior diameter (20g in Figure 10).
Similarly, the radius of the diffuser 20f in cylindrical air duct 20 can be along the circumferential direction variation in cylindrical air duct 20.Change speech It, diffuser 20f is not necessarily equipped with flat lower edge, i.e. its edge being directed toward from collector 20e as illustrated, and It is the lower edge with blunt circle.Preferably, it is hereinafter also referred to as the diffuser of " diffuser radius " for clarity The radius of 20f at least changing between the two in leading edge 20a, rear 20b, port side shoulder 20c and starboard side shoulder 20d.
Preferably, the diffuser radius 26a at leading edge 20a is selected in the range from 0 to 0.1*D, the expansion at rear 20b It dissipates device radius 26b to select in the range from 0 to 0.1*D, the diffuser at port side shoulder 20c and/or starboard side shoulder 20d Radius 26c is selected in the range from 0 to 0.1*D.Equally, as described above, D defines the diameter, preferably in cylindrical air duct 20 Be interior diameter (20g in Figure 10).
Fig. 9 shows that the protective case 6d in Fig. 5 to Fig. 8, protective case 6d limit cylindrical air duct 20, and cylindrical air duct 20 is preferably It is axially defined by collector 20e and diffuser 20f and includes leading edge 20a, rear 20b, port side shoulder 20c and starboard side shoulder Portion 20d.According to one aspect, leading edge 20a is provided with additional lifting surfaces 27.
Figure 10 shows that the protective case 6d in Fig. 5 to Fig. 8, protective case 6d limit cylindrical air duct 20, and cylindrical air duct 20 includes Leading edge 20a, rear 20b, port side shoulder 20c and starboard side shoulder 20d.Schematically, the diameter in cylindrical air duct 20 and more Particularly interior diameter D is indicated with reference numeral 20g.In addition, cylindrical air duct 20, the i.e. azimuth of protective case 6d (azimuth) ψ is indicated with reference numeral 20h.For example, it is assumed that the side clockwise along protective case 6d as shown azimuth ψ To definition, and meter makes ψ=0 at rear 20b from rear 20b.
Figure 11 shows that four exemplary cross sectionals of protective case 6d, protective case 6d limit cylindrical air duct 20, cylindrical air duct 20 It is preferably axially defined by collector 20e and diffuser 20f and includes leading edge 20a, rear 20b, port side shoulder 20c and the right side Topside shoulder 20d.Each section corresponds to the sectional view at the azimuth ψ that protective case 6d gives in Fig. 10.
More specifically, the first section view show the cutting line A-A in Figure 10 direction observation azimuth ψ= The exemplary cross sectional of protective case 6d at 180 °.First section view shows the leading edge 20a of protective case 6d, is provided with attached in Fig. 9 Add lifting surface 27.For example, collector 20e is arranged above with reference to as described in Fig. 8 at leading edge 20a and the top with rounding Edge, and diffuser 20f is schematically provided with flat lower edge.
Second section view shows the protective case 6d at azimuth ψ=0 ° of the direction observation of the cutting line A-A in Figure 10 Exemplary cross sectional.Second section view shows the rear 20b of protective case 6d.Such as and above with reference to described in Fig. 8, collector 20e is arranged at rear 20b and the top edge with rounding, and diffuser 20f is schematically provided with the lower edge of rounding.
Third section view shows the protective case at azimuth ψ=90 ° of the direction observation of the cutting line B-B in Figure 10 The exemplary cross sectional of 6d.The third section view shows the port side shoulder 20c of protective case 6d.For example, collector 20e above with reference to It is arranged at port side shoulder 20c and carries the top edge of rounding as described in Fig. 8, and diffuser 20f is schematically arranged There is flat lower edge.
4th section view shows the protective case at azimuth ψ=270 ° of the direction observation of the cutting line B-B in Figure 10 The exemplary cross sectional of 6d.4th section view shows the starboard side shoulder 20d of protective case 6d.For example, collector 20e above with reference to It is arranged at astarboard side shoulder 20d and carries the top edge of rounding as described in Fig. 8, and diffuser 20f is schematically arranged There is flat lower edge.
Figure 12 show the thrust in Fig. 5 and Fig. 6 according to the part (C) of Fig. 7 generate unit 3d, with protective case 6d, Upper rotor assemblies 7d and lower rotor assemblies 8d.Upper rotor assemblies 7d is around rotor axis 12e rotating operations and limits rotor plane 21, lower rotor assemblies 8d are around rotor axis 12d rotating operations and limit rotor plane 22.As described above, rotor axis 12e phases Rotor axis 12d is tilted.
More specifically, Figure 12 is shown controls the exemplary controlling party that thrust generates unit 3d for changing by RPM Method.In other words, if for example upper rotor assemblies 7d is run with the rotating speed Ω 2 of the rotating speed Ω 1 higher than lower rotor assemblies 8d, thrust Vector 23 is tilted with associated thrust orientation angle ε relative to exemplary reference plane 28a, thrust orientation angle ε reference numerals 28 indicate.As shown in the left side in Figure 12, as long as associated thrust orientation angle ε is less than 90 °, i.e. ε<90 °, in Fig. 1 to Fig. 4 Multi-rotor aerocraft 1 with regard to flight forward run.However, as shown in the right side in Figure 12, if associated thrust orientation angle ε Equal to 90 °, i.e. ε=90 °, the multi-rotor aerocraft 1 in Fig. 1 to Fig. 4 then hovers or vertical takeoff operation.
However, it is noted that the function additionally depends on the specific embodiment party of rotor assemblies 7d and lower rotor assemblies 8d Formula.More specifically, required speed discrepancy can be for example according to the pitch difference or rotor shaft between upper rotor assemblies and lower rotor assemblies Gradient between line 12e and rotor axis 12d etc. and change.However, detailed function is considered as those skilled in the art It is easy to get, therefore is not subject of the present invention.Therefore, it omits and it is described in more detail for clarity.
Figure 13 shows exemplary RPM biasings control diagram 29, shows the fortune of the multi-rotor aerocraft in Fig. 1 to Fig. 4 Row.Chart 29 includes schematically offline mode axis 29a and speed shaft 29b.
In chart 29, it is schematically shown that two curves 30,31.Curve 30 instantiates the upper rotor assemblies in Figure 12 The rotating speed Ω 2 of 7d, curve 31 instantiate the rotating speed Ω 1 of the lower rotor assemblies 8d in Figure 12.
As with indicated by arrow 32a, when the multi-rotor aerocraft 1 in Fig. 1 to Fig. 4 when operation starts, upper rotor group Part 7d is preferably run with rotating speed Ω 2, and rotating speed Ω 2 is less than the rotating speed Ω 1 of lower rotor assemblies 8d.Thus, it is upper in Fig. 1 to Fig. 4 Rotor craft 1 hovers with associated hovering mode operation, i.e..
Then, the rotating speed Ω 2 of upper rotor assemblies 7d preferably increases, and the rotating speed Ω 1 of lower rotor assemblies 8d preferably subtracts It is small.Then, as used indicated by arrow 32b, when upper rotor assemblies 7d is with the rotating speed Ω of the rotating speed Ω 1 higher than lower rotor assemblies 8d When 2 operation, the multi-rotor aerocraft 1 in Fig. 1 to Fig. 4 is run with associated forward flight mode.
Figure 14 shows that the protective case 6d in Fig. 5 to Figure 12, protective case 6d limit cylindrical air duct 20, and cylindrical air duct 20 includes Leading edge 20a, rear 20b, port side shoulder 20c and starboard side shoulder 20d.However, with the reality according to the protective case 6d of Fig. 5 to Figure 12 Mode is applied on the contrary, the rear 20b in existing cylinder air duct 20 at least substantially opens and is provided only with reinforcing element 33.Preferably, Cylindrical air duct 20 is opened at rear 20b with such as 30 ° to 60 ° of scheduled open-angle 33a, which, which corresponds to, reinforces The angle of strike of element 33.
Figure 15 show the thrust in Fig. 5 and Fig. 6 according to the part (C) of Fig. 7 generate unit 3d, with protective case 6d, Upper rotor assemblies 7d and lower rotor assemblies 8d.Protective case 6d includes leading edge 20a and rear 20b.Upper rotor assemblies 7d surrounds rotor shaft Line 12e rotating operations and restriction rotor plane 21, lower rotor assemblies 7d surround rotor axis 12d rotating operations and limit rotor and put down Face 22.
As described above, rotor axis 12e is tilted relative to rotor axis 12d.In fig.15, relative to horizontal reference plane 34 To illustrate the inclination.More specifically, rotor axis 12e with the associated inclination alpha that is marked with reference numeral 34a relative to water Flat reference planes 34 tilt, and rotor axis 12d is schematically perpendicular to horizontal reference plane 34, such as by with reference numeral 34b Come shown in the associated angle of inclination beta that indicates.
In addition, according to one aspect and with according to the embodiment of the protective case 6d of Fig. 5 to Figure 12 on the contrary, rear 20b is now equipped There is the wing flap 35 for being preferably designed to wing.Wing flap 35 can preferably surround associated rotation axis 35d and rotate, and with solid line It is shown in exemplary hovering position 35a, and is shown in dashed lines in exemplary flight forward position 35b.
Figure 16 shows that the thrust in Figure 15 generates the protective case 6d of unit 3d, and wing flap 35 is provided at rear 20b.Show Meaning property, wing flap 35 extends across angle of strike 35c, i.e. on angle of strike 35c at the rear 20b of protective case 6d.For example, wing flap 35 In its exemplary hovering position 35a being shown in Figure 15.
Figure 17 shows the protective case 6d that the thrust in Figure 15 generates unit 3d, and wing flap 35, root are provided at rear 20b According to Figure 16, wing flap 35 extends across angle of strike 35c, i.e. on angle of strike 35c at the rear 20b of protective case 6d.For example, wing flap 35 In its exemplary flight forward position 35b being now shown in Figure 15.
Finally, it is noted that the modification to aforementioned aspect of the present invention also belongs within the common sense of those skilled in the art, and Thus it is counted as the part of the present invention.
Reference numerals list
1 multi-rotor aerocraft
1a aircraft are longitudinal
1b aircraft are lateral
2 aircraft bodies
2a aircraft body internal volumes
2b aircraft body width
3 thrusts generate unit
3a, 3b, 3c, 3d thrust generate unit
4 thrusts generate cellular construction supporting member
4a, 4b, 4c, 4d thrust generate cellular construction supporting member
5 gear-box radome fairings
5a, 5b, 5c, 5d gear-box radome fairing
6 protective case units
6a, 6b, 6c, 6d protective case
Rotor assemblies on 7
The upper rotor assemblies of 7a, 7b, 7c, 7d
8 times rotor assemblies
Rotor assemblies under 8a, 8b, 8c, 8d
9 thrusts generate airflow direction
10 ground
10a is vertical or vertical reference line
11 vertical inclination angles
11a, 11b vertical inclination angle
12 rotor axis
12a, 12b, 12c, 12d rotor axis
13 cross dips
13a, 13b cross dip
The upper rotor assemblies engines of 14a
Rotor modular engine under 14b
The upper rotor assemblies direction of rotation 15a
Rotor assemblies direction of rotation under 15b
16 supporting structures
17 pitch variable quantities
The upper rotor assemblies rotor blade of 18a, 18b, 18c
Rotor assemblies rotor blade under 19a, 19b, 19c
20 air ducts
20a leading edges
20b rears
20c port side shoulders
20d starboard side shoulders
20e collectors
20f diffusers
The air ducts 20g interior diameter (D)
The air ducts 20h azimuth (ψ)
Rotor assemblies rotor plane on 21
The upper planar inclinations of 21a
22 times rotor assemblies rotor planes
22a lower planes inclination angle
23 thrust vectors
23a hovering airflow directions
23b flight forward airflow directions
The up-front total height in the air ducts 24a (HL)
The total height (HT) of the air ducts 24b rear
The total height (HS) of the air ducts 24c side shoulder
The collector radius (CRL) of the air ducts 25a edge
Collector radius (CRT) at the rear of the air ducts 25b
Collector radius (CRS) at the shoulder of the air ducts 25c side
The diffuser radius (DRL) of the air ducts 26a edge
Diffuser radius (DRT) at the rear of the air ducts 26b
Diffuser radius (DRS) at the shoulder of the air ducts 26c side
27 additional lifting surfaces
28 thrust orientation angles (ε)
28a reference planes
29 RPM bias control diagram
29a offline mode axis
29b rotating speeds
Rotor assemblies rotating speed (Ω 2) on 30
31 times rotor assemblies rotating speeds (Ω 1)
32a hovering patterns
32b forward flight modes
33 reinforcing elements
33a reinforcing element angle of strike
34 rotor assemblies tilt reference planes
The upper rotor assemblies inclination angles (α) of 34a
Rotor assemblies inclination angle (β) under 34b
35 wing flaps
35a wing flap hovering positions
35b wing flap flight forwards position
35c wing flap angle of strike
35d Flap rotation axis lines

Claims (15)

1. one kind generating unit (3d), including at least two rotor assemblies for generating the thrust of thrust along predetermined direction (23) (7d, 8d) and accommodate at most one protective case (6d) at least two rotor assemblies (7d, 8d), wherein the protective case (6d) defines cylindrical air duct (20), and the cylinder air duct is by air inlet region (20e) and air outlet area (20f) It axially defines, and wherein, the air inlet region (20e) has fluctuating in the circumferential direction of the cylindrical air duct (20) Geometry.
2. thrust according to claim 1 generates unit (3d),
It is characterized in that, axis of the height (24a, 24b, 24c) of the cylinder air duct (20) along the cylindrical air duct (20) To being limited between the air outlet area (20f) and the air inlet region (20e), the height is in the cylinder Change in the circumferential direction in shape air duct (20), wherein along the cylindrical air duct (20) circumferentially change the height (24a, 24b, 24c) define the geometry of the fluctuating of the air inlet region (20e).
3. thrust according to claim 2 generates unit (3d),
It is characterized in that, it leading edge (20a) and the rear that is diametrically opposed to one another that the cylinder air duct (20), which includes in the circumferential, (20b), and include port side shoulder (20c) and the starboard side shoulder (20d) being diametrically opposed to one another, wherein the port side shoulder (20c) and the starboard side shoulder (20d) respectively along cylindrical air duct (20) be arranged circumferentially in the leading edge (20a) with it is described Between rear (20b), and wherein, the height (24a) at the leading edge (20a) be less than the port side shoulder (20c) and/ Or the height (24c) at the starboard side shoulder (20d).
4. thrust according to claim 3 generates unit (3d),
It is characterized in that, the height (24b) at the rear (20b) is less than the port side shoulder (20c) and/or described The height (24c) at starboard side shoulder (20d).
5. thrust according to claim 3 generates unit (3d),
It is characterized in that, the height (24b) at the rear (20b) is less than the height at the leading edge (20a) (24a)。
6. thrust according to claim 3 generates unit (3d),
It is characterized in that, the height (24c) at the port side shoulder (20c) and/or the starboard side shoulder (20d) exists It is selected in range from 0.05*D to 0.5*D, wherein D defines the diameter (20g) of the cylindrical air duct (20).
7. thrust according to claim 3 generates unit (3d),
It is characterized in that, the air inlet region radius of the air inlet region (20e) of the cylinder air duct (20) (25a, 25b, 25c) changes in the circumferential direction of the cylindrical air duct (20), wherein the air inlet region radius (25a, 25b, 25c) in the leading edge (20a), the rear (20b), the port side shoulder (20c) and the starboard side shoulder At least changing between the two in (20d).
8. thrust according to claim 3 generates unit (3d),
It is characterized in that, the air outlet area radius of the air outlet area (20f) of the cylinder air duct (20) (26a, 26b, 26c) changes in the circumferential direction of the cylindrical air duct (20), wherein the air outlet area radius (26a, 26b, 26c) in the leading edge (20a), the rear (20b), the port side shoulder (20c) and the starboard side shoulder At least changing between the two in (20d).
9. thrust according to claim 3 generates unit (3d),
It is characterized in that, the rear (20b) of the cylinder air duct (20) at least opens and is provided with reinforcing element substantially (33)。
10. thrust according to claim 3 generates unit (3d),
It is characterized in that, the rear (20b) of the cylinder air duct (20) is equipped with wing flap (35).
11. thrust according to claim 3 generates unit (3d),
It is characterized in that, the leading edge (20a) of the cylinder air duct (20) is provided with additional lifting surfaces (27).
12. thrust according to claim 1 generates unit (3d),
It is characterized in that, the first rotor assemblies (7d) at least two rotor assemblies (7d) are arranged in the cylindrical wind Road (20) is external and adjacent to the air inlet region (20e) of the cylindrical air duct (20), wherein the protective case (6d) Accommodate the second rotor assemblies (8d) at least two rotor assemblies (8d).
13. thrust according to claim 12 generates unit (3d),
It is characterized in that, first rotor assemblies (7d) define the first rotor axis (12d), second rotor assemblies (8d) defines that the second rotor axis (12d), the first rotor axis (12d) and the second rotor axis (12d) are coaxial Arrangement.
14. thrust according to claim 13 generates unit (3d),
It is characterized in that, the first rotor axis (12d) and the second rotor axis (12d) are to be included in -60 ° to+60 ° Between range in associated inclination angle (21a, 22a) tilt.
15. a kind of multi-rotor aerocraft (1) includes at least one thrust production constructed according to any one of preceding claims Raw unit (3d).
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2024001143A1 (en) * 2022-06-30 2024-01-04 亿航智能设备（广州）有限公司 Ducted fan, aircraft and attitude control method and device therefor, and related apparatus

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107614379A (en) 2015-05-25 2018-01-19 多特瑞尔技术有限公司 Shield for aircraft
JP2020530913A (en) 2017-07-24 2020-10-29 ドテレル テクノロジーズ リミテッド Shroud
WO2019210128A2 (en) * 2018-04-27 2019-10-31 Aai Corporation Variable pitch rotor assembly for electrically driven vectored thrust aircraft applications
AU2019271730A1 (en) 2018-05-16 2020-12-24 Dotterel Technologies Limited Systems and methods for audio capture
EP3581491B1 (en) 2018-06-13 2020-06-24 AIRBUS HELICOPTERS DEUTSCHLAND GmbH A multirotor aircraft with a thrust producing unit that comprises an aerodynamically optimized shrouding
US10822080B2 (en) * 2018-06-28 2020-11-03 The Boeing Company Aircraft and methods of performing tethered and untethered flights using aircraft
US11027836B2 (en) * 2018-07-13 2021-06-08 The Boeing Company Rotorcraft with canted coaxial rotors
MX2021000277A (en) * 2018-07-23 2021-09-08 Airgility Inc System of play platform for multi-mission application spanning any one or combination of domains or environments.
JP7068126B2 (en) * 2018-10-01 2022-05-16 トヨタ自動車株式会社 Anomaly detection device and control device
WO2020219278A1 (en) * 2019-04-26 2020-10-29 Aergility Corporation Hybrid gyrodyne aircraft
KR102366194B1 (en) * 2020-03-26 2022-02-24 주식회사 풍산 Coaxial Rotor Flight
KR102337912B1 (en) * 2020-08-07 2021-12-10 한서대학교 산학협력단 Manufacturing method of propulsion unit for flight vehicle having rimfoil, propulsion unit for flight vehicle having rimfoil and flight vehicle
CN112520026A (en) * 2020-12-23 2021-03-19 中国民用航空飞行学院 Novel variant aircraft

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070034739A1 (en) * 2003-10-27 2007-02-15 Urban Aeronautics Ltd. Ducted fan VTOL vehicles
US20110001001A1 (en) * 2008-02-01 2011-01-06 Ashley Christopher Bryant Flying-wing aircraft
US20110147533A1 (en) * 2009-12-21 2011-06-23 Honeywell International Inc. Morphing ducted fan for vertical take-off and landing vehicle
CN102120489A (en) * 2011-02-28 2011-07-13 南昌航空大学 Tilt ducted unmanned aerial vehicle
CN102285449A (en) * 2011-06-07 2011-12-21 北京邮电大学 Coaxial double-rotor wing ducted aircraft
US20130206919A1 (en) * 2010-11-12 2013-08-15 Gabriel Shachor Systems and methods for controlling an aerial unit
CN104787316A (en) * 2015-04-17 2015-07-22 何春旺 Multi-rotor aircraft
CN104787315A (en) * 2015-04-17 2015-07-22 何春旺 Duct power device and aircraft
CN204956910U (en) * 2015-07-17 2016-01-13 优利科技有限公司 Rotorcraft
US20160009387A1 (en) * 2014-04-18 2016-01-14 Propulsive Wing, LLC Hybrid Axial/Cross-Flow Fan Multi-Rotor Aerial Vehicle

Family Cites Families (50)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB905911A (en) 1957-11-19 1962-09-12 Maurice Louis Hurel Improvements in aircraft having a lift producing rotor disposed in a supporting surface
US3584810A (en) 1969-05-08 1971-06-15 Gen Dynamics Corp Stacked rotor vtol aircraft
DE2434042C3 (en) 1974-07-16 1979-04-26 Dornier Gmbh, 7990 Friedrichshafen Vertical flying aircraft
US5152478A (en) 1990-05-18 1992-10-06 United Technologies Corporation Unmanned flight vehicle including counter rotating rotors positioned within a toroidal shroud and operable to provide all required vehicle flight controls
US5150857A (en) 1991-08-13 1992-09-29 United Technologies Corporation Shroud geometry for unmanned aerial vehicles
US5277381A (en) * 1992-08-12 1994-01-11 Piasecki Aircraft Corporation Rotary wing aircraft shrouded propeller sidewall thruster
JPH07125696A (en) * 1993-11-02 1995-05-16 Mitsubishi Heavy Ind Ltd Helicopter
US5575438A (en) * 1994-05-09 1996-11-19 United Technologies Corporation Unmanned VTOL ground surveillance vehicle
US6270038B1 (en) 1999-04-22 2001-08-07 Sikorsky Aircraft Corporation Unmanned aerial vehicle with counter-rotating ducted rotors and shrouded pusher-prop
GB2360752A (en) * 2000-04-01 2001-10-03 Glyn Jones Helicopter without tail rotor
US6568630B2 (en) 2001-08-21 2003-05-27 Urban Aeronautics Ltd. Ducted vehicles particularly useful as VTOL aircraft
US7032861B2 (en) 2002-01-07 2006-04-25 Sanders Jr John K Quiet vertical takeoff and landing aircraft using ducted, magnetic induction air-impeller rotors
USD543928S1 (en) 2003-01-23 2007-06-05 Ufoz, Llc Hovercraft with stacked rotor thruster and winglets
GB2389826B (en) * 2002-06-22 2006-08-23 John Edward Randell Craft propulsion
ITTO20030588A1 (en) 2003-07-30 2005-01-31 Fiat Ricerche FLYING CAR.
GB2409845A (en) * 2004-01-08 2005-07-13 Robert Graham Burrage Tilt-rotor aircraft changeable between vertical lift and forward flight modes
US9434471B2 (en) 2005-04-14 2016-09-06 Paul E Arlton Rotary wing vehicle
US20060226281A1 (en) 2004-11-17 2006-10-12 Walton Joh-Paul C Ducted fan vertical take-off and landing vehicle
WO2006069291A2 (en) * 2004-12-22 2006-06-29 Aurora Flight Sciences Corporation System and method for utilizing stored electrical energy for vtol aircraft thrust enhancement and attitude control
US7946528B2 (en) 2005-04-15 2011-05-24 Urban Aeronautics, Ltd. Flight control system especially suited for VTOL vehicles
DE102005022706A1 (en) 2005-05-18 2006-11-23 Dolch, Stefan, Dipl.-Ing. (FH) Helicopter especially for observation has multi rotor drive with rotor location outside the field of forward view of an onboard camera
US8720814B2 (en) * 2005-10-18 2014-05-13 Frick A. Smith Aircraft with freewheeling engine
CN101157385A (en) * 2007-11-27 2008-04-09 谭生 Helicopter
EP2234883B1 (en) 2007-12-14 2017-08-02 Urban Aeronautics Ltd. Vtol vehicle and method of operating
US8387911B2 (en) * 2008-07-25 2013-03-05 Honeywell International Inc. Ducted fan core for use with an unmanned aerial vehicle
US20120153087A1 (en) 2008-08-06 2012-06-21 Honeywell International Inc. Modular Pods for Use with an Unmanned Aerial Vehicle
US8240597B2 (en) * 2008-08-06 2012-08-14 Honeywell International Inc. UAV ducted fan lip shaping
CN201306711Y (en) 2008-11-04 2009-09-09 王国良 Environmentally-friendly energy-saving dimethyl ether special combustor
US8464978B2 (en) * 2009-04-16 2013-06-18 The Trustees Of The University Of Pennsylvania Counter-rotational inertial control of rotorcraft
US8733690B2 (en) 2009-08-24 2014-05-27 Joby Aviation, Inc. Lightweight vertical take-off and landing aircraft and flight control paradigm using thrust differentials
KR101169742B1 (en) 2009-11-20 2012-07-30 순천대학교 산학협력단 The flying object equipped coaxial duct system
KR101217804B1 (en) 2010-06-01 2013-01-22 (주)선택이앤티 Bottom propeller control type vehicle
NZ607121A (en) 2010-07-19 2015-02-27 Zee Aero Inc Personal aircraft
EP2551190B1 (en) * 2011-07-29 2013-11-20 AGUSTAWESTLAND S.p.A. Convertiplane
EP2551193B1 (en) 2011-07-29 2016-04-13 AGUSTAWESTLAND S.p.A. Convertiplane
EP2551198B1 (en) 2011-07-29 2013-11-13 AGUSTAWESTLAND S.p.A. Convertiplane
USD678169S1 (en) 2011-09-19 2013-03-19 Zee.Aero Inc. Aircraft
US8602942B2 (en) 2011-11-16 2013-12-10 Zee.Aero Inc. Centrifugal de-clutch
JP6037100B2 (en) * 2012-03-14 2016-11-30 株式会社Ihi Vertical take-off and landing aircraft
EP2738091B1 (en) 2012-11-30 2015-07-22 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Vertical take-off and landing (VTOL) aerial vehicle and method of operating such a VTOL aerial vehicle
CN103010463A (en) 2012-12-26 2013-04-03 南京航空航天大学 High-speed coaxial tilting double-rotor-wing flying wing machine
JP6108077B2 (en) * 2013-01-29 2017-04-05 株式会社Ihi Vertical take-off and landing aircraft
DE102013108207A1 (en) 2013-07-31 2015-02-05 E-Volo Gmbh Aircraft, especially multicopters
DE102013109392A1 (en) 2013-08-29 2015-03-05 Airbus Defence and Space GmbH Fast-flying, vertically launchable aircraft
US20150127209A1 (en) 2013-11-05 2015-05-07 King Fahd University Of Petroleum And Minerals Bird repellent system
DE102014213215A1 (en) * 2014-07-08 2016-01-14 Lilium GmbH whiz
KR101451646B1 (en) 2014-07-16 2014-10-16 (주)테크맥스텔레콤 The multi function for ducted type unmanned aircraft
WO2016136848A1 (en) * 2015-02-25 2016-09-01 株式会社プロドローン Multicopter
DE102015006511A1 (en) 2015-05-26 2016-12-01 Airbus Defence and Space GmbH Vertical launching aircraft
US10518880B2 (en) * 2017-02-16 2019-12-31 Amazon Technologies, Inc. Six degree of freedom aerial vehicle with a ring wing

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070034739A1 (en) * 2003-10-27 2007-02-15 Urban Aeronautics Ltd. Ducted fan VTOL vehicles
US20110001001A1 (en) * 2008-02-01 2011-01-06 Ashley Christopher Bryant Flying-wing aircraft
US20110147533A1 (en) * 2009-12-21 2011-06-23 Honeywell International Inc. Morphing ducted fan for vertical take-off and landing vehicle
US20130206919A1 (en) * 2010-11-12 2013-08-15 Gabriel Shachor Systems and methods for controlling an aerial unit
CN102120489A (en) * 2011-02-28 2011-07-13 南昌航空大学 Tilt ducted unmanned aerial vehicle
CN102285449A (en) * 2011-06-07 2011-12-21 北京邮电大学 Coaxial double-rotor wing ducted aircraft
US20160009387A1 (en) * 2014-04-18 2016-01-14 Propulsive Wing, LLC Hybrid Axial/Cross-Flow Fan Multi-Rotor Aerial Vehicle
CN104787316A (en) * 2015-04-17 2015-07-22 何春旺 Multi-rotor aircraft
CN104787315A (en) * 2015-04-17 2015-07-22 何春旺 Duct power device and aircraft
CN204956910U (en) * 2015-07-17 2016-01-13 优利科技有限公司 Rotorcraft

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2024001143A1 (en) * 2022-06-30 2024-01-04 亿航智能设备（广州）有限公司 Ducted fan, aircraft and attitude control method and device therefor, and related apparatus

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US20180244367A1 (en) 2018-08-30
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